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US 10,094,296 B2Granted
Gas turbine engine with rotor bore heating
AssigneeUnited Technologies Corporation
InventorsFrederick M. Schwarz, Paul W. Duesler
Life of this patent
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Abstract
A gas turbine engine has a compressor rotor with blades and a disk. A bore is defined radially inwardly of the disk. A combustor includes a burner nozzle. A tap taps air that has been combusted in the combustor section through a valve, and into the bore of the disk. A method is also disclosed.
Claims18
A gas turbine engine comprising:
- a compressor rotor including blades and a disk, with a bore defined radially inwardly of said disk;
- a combustor, including a burner nozzle;
- a tap for tapping air that has been combusted in the combustor through a valve, and into said bore of said disk;
- said valve is controlled to only be opened under certain periods of operation of the gas turbine engine;
- and
- a control for said valve is programmed to be open when an aircraft associated with the gas turbine engine is at idle and to be closed at take-off.
3 more elements
A gas turbine engine comprising:
- a compressor rotor including blades and a disk, with a bore defined radially inwardly of said disk;
- a combustor, including a burner nozzle;
- a tap for tapping air that has been combusted in the combustor through a valve, and into said bore of said disk;
- and
- said tapped air is jacketed in a jacket of compressed air.
2 more elements
A method of operating a gas turbine engine comprising:
- tapping air that has been combusted in a combustor section through a valve, and into a bore of a disk of a compressor rotor;
- said valve is opened only under certain periods of operation of the gas turbine engine;
- and
- said valve is opened when an aircraft associated with the gas turbine engine is at idle and is closed at take-off.
1 more element
Dependencies are inferred from the claim text.